(19)
(11) EP 3 854 991 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
04.08.2021 Bulletin 2021/31

(43) Date of publication A2:
28.07.2021 Bulletin 2021/30

(21) Application number: 21150440.2

(22) Date of filing: 06.01.2021
(51) International Patent Classification (IPC): 
F01D 5/18(2006.01)
 B22F 5/04(2006.01)
(84) Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
Designated Extension States:
BA ME
Designated Validation States:
KH MA MD TN

(30) Priority: 22.01.2020 US 202016749143

(71) Applicant: General Electric Company
Schenectady, NY 12345 (US)

(72) Inventors:
  • SNIDER, Zachary John
    Greenville, SC South Carolina 29615 (US)
  • VANTASSEL, Brad Wilson
    Greenville, SC South Carolina 29615 (US)
  • JONES, Jeffrey Clarence
    Greenville, SC South Carolina 29681 (US)

(74) Representative: Openshaw & Co. 
8 Castle Street
Farnham, Surrey GU9 7HR
Farnham, Surrey GU9 7HR (GB)

   


(54) TURBINE ROTOR BLADE


(57) A turbine rotor blade (120) is additively manufactured and includes an airfoil body (122) with a radially extending chamber (134) for receiving a coolant flow (136), a tip end (140) at a radial outer end (142) of the airfoil body (122), and a shank (148, 148A) at a radial inner end (152) of the airfoil body (122). The radially extending chamber (134) extends at least partially into the shank (148, 148A) to define a shank inner surface (154). An integral impingement cooling structure (160) is within the radially extending chamber (134). The integral impingement cooling structure (160) allows an exterior surface (170) of a hollow body (162) thereof to be uniformly spaced from the airfoil inner surface (132) despite the curvature of the chamber (134). The turbine rotor blade (120) has impingement cooling (160) throughout the blade (120).







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Search report